Robust Hinf spacecraft pointing control method and system based on feature structure configuration
A characteristic structure and pointing control technology, applied in the field of satellite control, can solve the problems of affecting communication business work, long steady-state response time, affecting payload pointing steady-state time, etc.
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[0143] Simulation conditions: The spacecraft in geostationary orbit has three large flexible attachments: 2 solar wings and 1 ultra-large flexible mesh antenna with an arm length of more than ten meters and a reflector diameter of more than ten meters. Among them, the The fundamental frequency is about 0.1Hz, and the fundamental frequency of the large flexible mesh antenna is about 0.12Hz. The flexible mode of the solar wing takes the 6th order, and the flexible mode of the large flexible mesh antenna takes the 10th order. The moment of inertia of the rolling axis is
[0144] I x =19000kg·m 2
[0145] The disturbance bound function is determined, and the uncertain model part Δ M The frequency domain characteristics of figure 2 (Frequency Domain Characteristic Curve of Uncertain Model of Flexible Part) is shown. According to the uncertain model, the expected multiplicative model disturbance bound function (5) of the rolling direction we designed is T 1 =130,T 2 =140,D ...
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